Method, device, equipment and medium for constructing mass distribution of structural finite element model of aircraft

Abstract

The present application discloses a method, device, equipment and medium for constructing a mass distribution of a structural finite element model of an aircraft, and relates to the technical field of aircraft structural analysis, including: obtaining mass point data of a component to be analyzed of an aircraft and a corresponding finite element model file; determining a target interpolation function according to the mass point data and the interpolation function format, calculating the initial mass distribution of each finite element node through the target interpolation function and according to the finite element model file; calculating the total mass of the finite element model according to the initial mass distribution, calculating the actual total mass based on the mass point data, calculating the first modeling error according to the total mass of the finite element model and the actual total mass, calculating the second modeling error of the center of mass, and calculating the third modeling error of the moment of inertia; performing gradient calculation on the finite element model information corresponding to the modeling error that does not meet the error requirements, and adjusting the initial mass of the node using the gradient information until the modeling requirements are met. The accuracy and reliability of the mass distribution modeling results are guaranteed.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft structure analysis, and in particular to a method, device, equipment and medium for constructing a mass distribution of a structural finite element model of an aircraft. Background Art

[0002] In the process of establishing a traditional structural finite element model, if a finite element model with high geometric restoration is established based on the original geometric shape of the component, the mass distribution of the component can be naturally obtained according to the material density, and the mass of each unit can be automatically distributed to the node to form a mass matrix for solution. However, in practical applications, especially in the aerodynamic / structural coupling analysis of aircraft, the use of a finite element model with high geometric restoration will inevitably make the number of model nodes and units too large and the calculation scale seriously exceeded. Therefore, in practical applications, a simplified structural model based on a certain equivalent principle is usually used.

[0003] However, for this type of simplified / equivalent finite element model, it is impossible to obtain the correct component mass distribution through the actual material density. It is necessary to restore the mass distribution of the component finite element model based on the measured mass distribution through concentrated mass units, equivalent material density, etc. At present, the restoration process of this type of mass distribution relies on manual assignment, which is not only time-consuming and labor-intensive, but the specific concentrated mass / equivalent material density value also depends on the experience of the assigner, and it is difficult to ensure sufficient accuracy and reliability. Therefore, it is necessary to develop an automated, high-fidelity finite element mass distribution modeling method to reduce the workload of manual processing, improve the overall efficiency of aircraft aerodynamic / structural coupling analysis, and greatly improve the accuracy and reliability of mass distribution parameters. Summary of the invention

[0004] In view of this, the purpose of the present invention is to provide a method, device, equipment and medium for constructing a mass distribution of a structural finite element model of an aircraft, which can realize automated and high-fidelity finite element mass distribution modeling. The specific scheme is as follows:

[0005] In a first aspect, the present application discloses a method for constructing a mass distribution of a structural finite element model of an aircraft, comprising:

[0006] Acquire mass point data of each mass point on the component to be analyzed of the aircraft and a finite element model file corresponding to the component to be analyzed; wherein the mass point is a discrete point used to characterize the inertia parameter and mass distribution of the component to be analyzed;

[0007] Determining a target interpolation function according to the mass point data and the interpolation function format, so as to calculate the initial mass distribution of each finite element node according to the target interpolation function and the spatial coordinate information of each finite element node in the finite element model file;

[0008] Calculating the total mass of the finite element model of the component to be analyzed according to the initial mass distribution, and calculating the actual total mass of the component to be analyzed based on the mass point data, so as to calculate a first modeling error according to the total mass of the finite element model and the actual total mass, calculate a second modeling error according to the center of mass of the finite element model of the component to be analyzed and the actual center of mass, and calculate a third modeling error according to the moment of inertia of the finite element model of the component to be analyzed and the actual moment of inertia;

[0009] The finite element model information corresponding to the modeling error that does not meet the corresponding error requirement is gradient calculated to adjust the node initial mass of each finite element node according to the corresponding gradient information, and then jump to execute the step of calculating the first modeling error according to the total mass of the finite element model and the actual total mass until each modeling error meets the corresponding modeling requirement, and outputs the target mass distribution result of each corresponding finite element node;

[0010] Among them, the modeling error that does not meet the corresponding error requirement is any one or more of the first modeling error greater than a first error threshold, the second modeling error greater than a second error threshold, and the third modeling error greater than a third error threshold.

[0011] Optionally, the step of obtaining mass point data of each mass point on a component to be analyzed of the aircraft and a finite element model file corresponding to the component to be analyzed includes:

[0012] Obtaining the quantity information, actual mass information, and spatial coordinate information of each mass point on the component to be analyzed of the aircraft;

[0013] A finite element model file corresponding to the component to be analyzed is obtained, so as to read the quantity information and the spatial coordinate information of each finite element node from the finite element model file.

[0014] Optionally, determining a target interpolation function according to the mass point data and an interpolation function format, so as to calculate an initial mass distribution of each finite element node by using the target interpolation function and according to spatial coordinate information of each finite element node in the finite element model file, comprises:

[0015] Substituting the spatial coordinate information and the actual mass information of each mass point into the interpolation function format to determine the target interpolation function;

[0016] The spatial coordinate information of each of the finite element nodes is substituted into the target interpolation function to calculate the initial mass distribution of each of the finite element nodes.

[0017] Optionally, calculating the total mass of the finite element model of the component to be analyzed according to the initial mass distribution, and calculating the actual total mass of the component to be analyzed based on the mass point data, includes:

[0018] Accumulating the masses of each initial node in the initial mass distribution to calculate the total mass of the finite element model of the component to be analyzed; calculating the actual total mass of the component to be analyzed based on the actual mass information of each mass point;

[0019] Calculate the model centroid coordinates of the finite element model using the mass of each of the initial nodes, the spatial coordinate information of each of the finite element nodes, and the total mass of the finite element model; calculate the actual centroid coordinates of the component to be analyzed using the actual mass information of each of the mass points, the spatial coordinate information of each of the mass points, and the actual total mass;

[0020] The finite element model moment of inertia of the component to be analyzed is calculated using the mass of each of the initial nodes, the spatial coordinate information of each of the finite element nodes, and the model center of mass coordinates; the actual moment of inertia of the component to be analyzed is calculated using the actual mass information of each of the mass points, the spatial coordinate information of each of the mass points, and the actual center of mass coordinates.

[0021] Optionally, the first modeling error is calculated according to the total mass of the finite element model and the actual total mass, the second modeling error is calculated according to the center of mass of the finite element model of the component to be analyzed and the actual center of mass, and the third modeling error is calculated according to the moment of inertia of the finite element model of the component to be analyzed and the actual moment of inertia, including:

[0022] Performing a difference processing on the total mass of the finite element model and the actual total mass to obtain a first modeling error;

[0023] Performing a difference process on the model centroid coordinates and the actual centroid coordinates to obtain a second modeling error;

[0024] The finite element model moment of inertia and the actual moment of inertia are subjected to difference processing to obtain a third modeling error.

[0025] Optionally, the method for constructing mass distribution of a structural finite element model of an aircraft further includes:

[0026] When stiffness information and damping information exist in the finite element model file, solving the modal analysis result of the finite element model of the component to be analyzed;

[0027] performing a difference process on the modal analysis result of the finite element model and the actual modal analysis result to obtain a fourth modeling error;

[0028] Accordingly, the finite element model information corresponding to the modeling error that does not meet the corresponding error requirement is subjected to gradient calculation to adjust the node initial quality of each finite element node according to the corresponding gradient information, including:

[0029] The finite element model information corresponding to the fourth modeling error that does not meet the corresponding error requirement is subjected to gradient calculation, so as to adjust the node initial quality of each finite element node according to the corresponding gradient information.

[0030] Optionally, adjusting the initial node quality of each finite element node according to the corresponding gradient information includes:

[0031] Calculate a corresponding quality requirement adjustment amount based on a modeling error corresponding to the gradient information and the gradient information;

[0032] The mass requirement adjustment amount is weighted averaged to obtain a corresponding target mass requirement adjustment amount; and the node initial mass of each finite element node is adjusted according to the target mass requirement adjustment amount.

[0033] In a second aspect, the present application discloses a device for constructing a mass distribution of a structural finite element model of an aircraft, comprising:

[0034] An information acquisition module, used to acquire mass point data of each mass point on the component to be analyzed of the aircraft and a finite element model file corresponding to the component to be analyzed; wherein the mass point is a discrete point used to characterize the inertia parameter and mass distribution of the component to be analyzed;

[0035] an initial calculation module, used to determine a target interpolation function according to the mass point data and the interpolation function format, so as to calculate the initial mass distribution of each finite element node according to the target interpolation function and the spatial coordinate information of each finite element node in the finite element model file;

[0036] an error acquisition module, configured to calculate the total mass of the finite element model of the component to be analyzed according to the initial mass distribution, and calculate the actual total mass of the component to be analyzed based on the mass point data, so as to calculate a first modeling error according to the total mass of the finite element model and the actual total mass, calculate a second modeling error according to the centroid of the finite element model of the component to be analyzed and the actual centroid, and calculate a third modeling error according to the moment of inertia of the finite element model of the component to be analyzed and the actual moment of inertia;

[0037] A quality adjustment module is used to perform gradient calculation on the finite element model information corresponding to the modeling error that does not meet the corresponding error requirements, so as to adjust the initial node mass of each finite element node according to the corresponding gradient information, and then jump to execute the step of calculating the first modeling error according to the total mass of the finite element model and the actual total mass until each modeling error meets the corresponding modeling requirements, and output the corresponding target mass distribution results of each finite element node; wherein the modeling error that does not meet the corresponding error requirements is any one or more of the first modeling error greater than the first error threshold, the second modeling error greater than the second error threshold, and the third modeling error greater than the third error threshold.

[0038] In a third aspect, the present application discloses an electronic device, comprising:

[0039] Memory, used to store computer programs;

[0040] The processor is used to execute the computer program to implement the steps of the method for constructing the mass distribution of the structural finite element model of the aircraft disclosed above.

[0041] In a fourth aspect, the present application discloses a computer-readable storage medium for storing a computer program; wherein, when the computer program is executed by a processor, the steps of the method for constructing a mass distribution of a structural finite element model of an aircraft disclosed above are implemented.

[0042] It can be seen that the present application discloses a method for constructing a mass distribution of a structural finite element model of an aircraft, comprising: obtaining mass point data of each mass point on a component to be analyzed of the aircraft and a finite element model file corresponding to the component to be analyzed; wherein the mass point is a discrete point used to characterize the inertia parameters and mass distribution of the component to be analyzed; determining a target interpolation function according to the mass point data and an interpolation function format, so as to calculate the initial mass distribution of each finite element node through the target interpolation function and according to the spatial coordinate information of each finite element node in the finite element model file; calculating the total mass of the finite element model of the component to be analyzed according to the initial mass distribution, and calculating the actual total mass of the component to be analyzed based on the mass point data, so as to calculate a first modeling error according to the total mass of the finite element model and the actual total mass, and calculating the first modeling error according to the total mass of the finite element model and the actual total mass of the component to be analyzed. The method comprises the following steps: calculating a second modeling error according to the centroid of the finite element model of the component to be analyzed and the actual centroid, calculating a third modeling error according to the moment of inertia of the finite element model of the component to be analyzed and the actual moment of inertia; performing gradient calculation on the finite element model information corresponding to the modeling error that does not meet the corresponding error requirement, so as to adjust the node initial mass of each finite element node according to the corresponding gradient information, and then jumping to execute the step of calculating the first modeling error according to the total mass of the finite element model and the actual total mass, until each modeling error meets the corresponding modeling requirement, and outputting the target mass distribution result of each corresponding finite element node; wherein the modeling error that does not meet the corresponding error requirement is any one or more of the first modeling error greater than the first error threshold, the second modeling error greater than the second error threshold, and the third modeling error greater than the third error threshold. It can be seen that through the target interpolation method, based on the given mass distribution measurement results, the corresponding finite element model node mass distribution results are calculated; and based on the conservation of the overall mass and moment of inertia of the model, the accuracy and reliability of the distribution results are determined; at the same time, based on the determination results, the mass distribution is fine-tuned and iterated until the accuracy meets the analysis requirements, and the use of interpolation and iterative fine-tuning realizes the automatic calculation and allocation of finite element mass distribution, which greatly improves the efficiency of structural finite element dynamics solution and its solution in aerodynamic / structural coupling analysis applications; by determining the accuracy of the distribution results based on a variety of mass distribution accuracy criteria and performing iterative fine-tuning accordingly, the accuracy and reliability of the mass distribution modeling results are guaranteed. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.

[0044] Figure 1A flow chart of a method for constructing a mass distribution of a structural finite element model of an aircraft disclosed in the present application;

[0045] Figure 2 A quality point diagram of an input disclosed in the present application;

[0046] Figure 3 A corresponding finite element model diagram of an input disclosed in this application;

[0047] Figure 4 A diagram of an initial mass distribution model disclosed in this application;

[0048] Figure 5 A diagram of a precisely constructed mass distribution model disclosed in this application;

[0049] Figure 6 A flowchart of a method for constructing accurate mass distribution of a structural finite element model of a specific aircraft disclosed in this application;

[0050] Figure 7 A schematic diagram of a mass distribution construction device for a structural finite element model of an aircraft disclosed in the present application;

[0051] Figure 8 This is a structural diagram of an electronic device disclosed in this application. DETAILED DESCRIPTION

[0052] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0053] With the development and application of aerodynamic / structural coupling numerical simulation technology based on computational fluid dynamics (CFD) and computational structural dynamics (CSD), it has gradually played a key role in the design, analysis, optimization and evaluation of aerospace vehicles. The computational structural mechanics part usually uses finite element analysis (FEA) or derivative methods based on finite elements. This method divides the complex component to be analyzed into a finite number of units with relatively simple geometric shapes, and uses the displacement of nodes or interpolation points inside / on the boundary of the unit to characterize the deformation of the unit, thereby obtaining the overall deformation field distribution of the component.

[0054] In the structural finite element dynamics analysis, it is necessary to allocate the mass of each finite element node in the finite element model according to the mass distribution of the component to be analyzed, and then obtain the mass matrix for dynamic solution. This mass matrix corresponds to the coefficient matrix of the second-order derivative of the node displacement (i.e., the acceleration term), which is indispensable in the dynamic solution.

[0055] In the process of establishing a traditional structural finite element model, if a finite element model with high geometric restoration is established based on the original geometric shape of the component, the mass distribution of the component can be naturally obtained according to the material density, and the mass of each unit can be automatically distributed to the node to form a mass matrix for solution. However, in practical applications, especially in the aerodynamic / structural coupling analysis of aircraft, the use of a finite element model with high geometric restoration will inevitably make the number of model nodes and units too large and the calculation scale seriously exceeded. Therefore, in practical applications, a simplified structural model based on a certain equivalent principle is usually used.

[0056] However, for this type of simplified / equivalent finite element model, it is impossible to obtain the correct component mass distribution through the actual material density. It is necessary to restore the mass distribution of the component finite element model based on the measured mass distribution through concentrated mass units, equivalent material density, etc. At present, the restoration process of this type of mass distribution relies on manual assignment, which is not only time-consuming and labor-intensive, but the specific concentrated mass / equivalent material density value also depends on the experience of the assigner, and it is difficult to ensure sufficient accuracy and reliability. Therefore, it is necessary to develop an automated, high-fidelity finite element mass distribution modeling method to reduce the workload of manual processing, improve the overall efficiency of aircraft aerodynamic / structural coupling analysis, and greatly improve the accuracy and reliability of mass distribution parameters.

[0057] To this end, the present invention provides a solution for constructing a mass distribution of a structural finite element model of an aircraft, which can realize automated and high-fidelity finite element mass distribution modeling.

[0058] Reference Figure 1 As shown, an embodiment of the present invention discloses a method for constructing a mass distribution of a structural finite element model of an aircraft, comprising:

[0059] Step S11: obtaining mass point data of each mass point on the component to be analyzed of the aircraft and a finite element model file corresponding to the component to be analyzed; wherein the mass point is a discrete point used to characterize the inertia parameters and mass distribution of the component to be analyzed.

[0060] For the current scenario where aerodynamic / structural coupling is required, the structural finite element model and mass distribution input can be used for any given structure, and an accurate finite element node mass distribution that meets the requirements can be given based on the solution of this application. This application uses aircraft components as an example to illustrate this solution.

[0061] In this embodiment, the quantity information, actual mass information, and spatial coordinate information of each mass point on the aircraft component to be analyzed are obtained. It can be understood that, for the current scenario where aerodynamic / structural coupling is required, taking aircraft components as an example, if there is a request for restoring the mass distribution of the finite element model of the aircraft component, the corresponding mass distribution parameters are required. Therefore, the component to be analyzed involved in the current request is determined, and the mass point data of each mass point on the component to be analyzed is obtained, where the mass points of the aircraft component to be analyzed are as follows: Figure 2 As shown in the figure, the mass point data is obtained by sampling, but the sampling results are not used directly, and the mass point data is characterized as a set of given discrete points with a certain number, mass and spatial position, which are used to characterize the mass, center of mass, moment of inertia and other inertial parameters of the component to be analyzed, as well as the specific mass distribution. Specifically, the mass point data includes the quantity information of the mass points, the actual mass information of each mass point and the spatial coordinate information of each mass point. Indicates the quantity information of quality points, Indicates the quality point number, the value is ; for quality points, and the corresponding actual quality information is , the spatial coordinate information is .

[0062] In this embodiment, the finite element model file corresponding to the component to be analyzed is obtained to read the quantity information and spatial coordinate information of each finite element node from the finite element model file. It can be understood that the finite element grid point parameters are obtained by reading the corresponding finite element model file and also belong to the input content. Therefore, it is necessary to obtain the finite element model file corresponding to the current component to be analyzed, such as Figure 3 As shown in FIG. 1 , the finite element grid point parameters specifically include the quantity information of each finite element node and the spatial coordinate information of each finite element node. Indicates the quantity information of each finite element node, Indicates the finite element node number, the value is ; for Finite element nodes, whose spatial coordinate information is , and the corresponding mass of each finite element node to be solved is .

[0063] Step S12: determining a target interpolation function according to the mass point data and the interpolation function format, so as to calculate the initial mass distribution of each finite element node through the target interpolation function and according to the spatial coordinate information of each finite element node in the finite element model file.

[0064] In this embodiment, the spatial coordinate information and actual mass information of each mass point are substituted into the interpolation function format to determine the target interpolation function; the spatial coordinate information of each finite element node is substituted into the target interpolation function to calculate the initial mass distribution of each finite element node. It can be understood that the initial mass distribution of each node is obtained by the interpolation method. The function interpolation format may specifically include but is not limited to: Lagrange interpolation, Newton interpolation, Hermite interpolation, spline interpolation, inverse weighted average interpolation, radial basis interpolation, etc. By inputting the mass point data As control points, interpolation is used to obtain the mass distribution / density interpolation function of the model , which is the target interpolation function, and finally the spatial coordinates of the finite element nodes Substituting the target interpolation function, we can get the initial mass distribution of each node ,like Figure 4 shown.

[0065] Step S13: Calculate the total mass of the finite element model of the component to be analyzed according to the initial mass distribution, and calculate the actual total mass of the component to be analyzed based on the mass point data, so as to calculate the first modeling error according to the total mass of the finite element model and the actual total mass, calculate the second modeling error according to the center of mass of the finite element model of the component to be analyzed and the actual center of mass, and calculate the third modeling error according to the moment of inertia of the finite element model of the component to be analyzed and the actual moment of inertia.

[0066] In this embodiment, the masses of each initial node in the initial mass distribution are accumulated to calculate the total mass of the finite element model of the component to be analyzed; the actual total mass of the component to be analyzed is calculated based on the actual mass information of each mass point. It can be understood that the initial mass distribution of each finite element node obtained by interpolation calculation is accumulated, and the accumulation formula is as follows:

[0067] ;

[0068] In this way, the total mass of the finite element model is accumulated . Compare it with the actual total mass of the component to be analyzed In comparison, the actual total mass Usually obtained by measurement. If not provided, it can be calculated using the following formula:

[0069] ;

[0070] In this embodiment, the total mass of the finite element model is subtracted from the actual total mass to obtain the first modeling error. It can be understood that by calculating the total mass of the finite element model The actual total mass The difference between them is used to obtain the error between the two, that is, the first modeling error, which is used to determine whether the modeling accuracy meets the requirements.

[0071] In this embodiment, the model centroid coordinates of the finite element model are calculated using the mass of each initial node, the spatial coordinate information of each finite element node, and the total mass of the finite element model; the actual centroid coordinates of the component to be analyzed are calculated using the actual mass information of each mass point, the spatial coordinate information of each mass point, and the actual total mass; the model centroid coordinates and the actual centroid coordinates are subjected to difference processing to obtain the second modeling error. It can be understood that using the obtained initial mass distribution The initial node mass of each finite element node is used as the weight, and the weighted average of the spatial coordinate information of each finite element node is calculated to obtain the model centroid coordinates of the finite element model , where the coordinates of the model centroid of the finite element model are calculated as follows:

[0072] ;

[0073] Then, the model coordinates of the obtained finite element model are The actual centroid coordinates of the component to be analyzed By comparison, the spatial position coordinates of the actual center of mass are obtained by measurement. If not measured, they can be obtained by calculating the weighted average of the input mass point coordinates. The formula is as follows:

[0074] ;

[0075] Then, calculate the coordinates of the model center of mass of the finite element model The actual centroid coordinates The difference between the two is obtained by taking the error between them, that is, the second modeling error, which is used to determine whether the modeling accuracy meets the requirements.

[0076] In this embodiment, the finite element model moment of inertia of the component to be analyzed is calculated using the initial node mass, the spatial coordinate information of each finite element node, and the model centroid coordinates; the actual moment of inertia of the component to be analyzed is calculated using the actual mass information of each mass point, the spatial coordinate information of each mass point, and the actual centroid coordinates, so as to perform a difference processing between the finite element model moment of inertia and the actual moment of inertia to obtain a third modeling error. It can be understood that the X, Y, and Z three-axis moment of inertia of the finite element model, that is, the moment of inertia of the finite element model, is obtained by using the initial node mass of each finite element node, combined with the spatial coordinate information of each finite element node and the model centroid coordinates. The specific calculation method is:

[0077] ;

[0078] The above calculation of the finite element model moment of inertia The actual moment of inertia of the component to be analyzed By comparison, the moment of inertia is obtained by measurement, and if not available it can be calculated as follows:

[0079] ;

[0080] Then, calculate the moment of inertia of the finite element model The actual moment of inertia The difference between them is used to obtain the error between the two, that is, the third modeling error, which is used to determine whether the modeling accuracy meets the requirements.

[0081] In order to further improve the modeling accuracy, the fourth modeling error can be further calculated based on the error calculation of the above-mentioned first modeling error, the second modeling error, and the third modeling error. Specifically, when there is stiffness information and damping information in the finite element model file, the modal analysis results of the finite element model of the component to be analyzed are solved; the modal analysis results of the finite element model are subtracted from the actual modal analysis results to obtain the fourth modeling error; it can be understood that the current finite element model is first required to be a model with reliable stiffness and damping, and then the finite element modal solution function is used to first calculate the eigenvalues ​​and eigenvectors of the stiffness matrix, and then obtain the modal analysis results of the finite element model. Each solved mode has a characteristic frequency, that is, the modal frequency. Different modes are sorted in order from low to high according to the modal frequency, and a certain number of modes that are ranked first are taken as the first. represents the total order of the modes taken, represents the modal order number, Indicates The modal frequency, Indicates The first-order mode vibration shape, for the finite element, contains the orthogonalized displacement amplitude of each node corresponding to the first-order mode, Indicates The displacement vector of a node is The dynamic response of the finite element model under load or disturbance conditions can be regarded as the superposition of all modal vibrations or approximation of the previous The superposition of the order modes, so the modal frequency of the finite element model The actual modal frequency , and the finite element vibration mode The actual vibration mode The difference between them can be used as an important basis for the accuracy of mass distribution modeling, that is, the fourth modeling error. In addition, for models with incomplete boundary condition constraints, the overall rigid body motion can occur at this time. For such moving parts, their modes will also contain rigid body modes corresponding to rigid body motion, with a maximum number of 6 orders. The numerical feature of these rigid body modes is that the theoretical value of the modal frequency is zero. These rigid body modes should be excluded in the actual analysis process.

[0082] Step S14: performing gradient calculation on the finite element model information corresponding to the modeling error that does not meet the corresponding error requirements, so as to adjust the initial node mass of each finite element node according to the corresponding gradient information, and then jumping to execute the step of calculating the first modeling error according to the total mass of the finite element model and the actual total mass, until each modeling error meets the corresponding modeling requirements, and outputting the corresponding target mass distribution results of each finite element node; wherein the modeling error that does not meet the corresponding error requirements is any one or more of the first modeling error greater than the first error threshold, the second modeling error greater than the second error threshold, and the third modeling error greater than the third error threshold.

[0083] In this embodiment, in the above-mentioned modeling error calculation process, the gradient of the finite element model information (total mass of the finite element model, center of mass of the finite element model, moment of inertia of the finite element model) corresponding to the modeling error that does not meet the corresponding error requirement relative to the initial node mass of each finite element node is used to calculate the fine-tuning value of the subsequent iteration. Specifically, based on the modeling error corresponding to the gradient information and the gradient information, the corresponding mass requirement adjustment amount is calculated; the total mass of the finite element model is used as the gradient. Take the specific calculation method as an example. First, calculate the total mass of the finite element model. Relative to the initial node mass The partial derivative of , then the corresponding gradient information is After obtaining the gradient information, based on the difference between the actual total mass and the model total mass , we can get the mass demand adjustment of each node based on the total mass: Similarly, the required mass adjustment of each node based on the centroid of the finite element model can be obtained: , , , and the required adjustment based on the moment of inertia of the finite element model , , .

[0084] Furthermore, the mass demand adjustment amount is weighted averaged to obtain the corresponding target mass demand adjustment amount; the initial mass of each finite element node is adjusted according to the target mass demand adjustment amount. It can be understood that the target adjustment amount used in the actual iteration process is the weighted average of the above-mentioned demand adjustment amounts, and the average weight can be taken as the relative error of the corresponding design variable. After obtaining the final adjustment amount, the quality of each node is adjusted. Make corresponding increases or decreases.

[0085] In this embodiment, based on the modeling accuracy requirement, if there is a fourth modeling error in the modeling error, the finite element model information corresponding to the fourth modeling error that does not meet the corresponding error requirement is subjected to gradient calculation, so as to adjust the node initial mass of each finite element node according to the corresponding gradient information. It can be understood that for the fourth modeling error that does not meet the requirement, the modal analysis result of the finite element model that does not meet the requirement is subjected to corresponding calculation. Specifically, For the first-order mode, the demand adjustment can be calculated by the following formula:

[0086] ;

[0087] in, is the displacement vector of the corresponding finite element node in the actual vibration mode.

[0088] In this embodiment, the adjusted finite element model mass distribution obtained after each adjustment is used as the initial mass distribution, and the steps of calculating the first modeling error, the second modeling error, and the like are performed again until the adjusted finite element model mass distribution meets the modeling error requirements, and the mass distribution result of the current finite element node is output as the target mass distribution result, such as Figure 5 As shown in the figure, the target mass distribution results can be written into a separate text file or directly into the corresponding finite element model file according to actual requirements.

[0089] Reference Figure 6 As shown, the present invention specifically discloses a process for constructing an accurate mass distribution of a structural finite element model of an aircraft wing:

[0090] Step (1): Read the mass point information in the form of mass points of the aircraft wing, that is, the mass distribution input, which contains a total of 16 mass points. The actual mass information of each mass point is: , for which mass points, the corresponding spatial coordinates are .

[0091] Step (2): Read the finite element mesh nodes, which have a total of 49 nodes. finite element nodes, whose spatial coordinates are .

[0092] Step (3): Use the interpolation method to obtain the initial mass distribution of each node. This embodiment uses the radial basis interpolation method. First, based on the number of control points (i.e., the mass points input above, the same below), define Kernel Function ,in is the distance between the function point and the control point, that is ; The target interpolation function can be expressed as the weighted average of all 16 kernel functions, that is, ,in is the weight of the corresponding kernel function. To solve this set of weights, all control points need to be substituted into the equation ,get:

[0093] ;

[0094] in, Indicates Control point to The distance between the control points. Solving this system of equations can obtain the required weights, and then obtain the interpolation function It should be noted that the interpolation function obtained by directly substituting the mass of the mass point cannot be used directly, because the mass of each mass point actually represents the total mass in a certain volume nearby. Therefore, the density should be used as the function value in the interpolation process. However, the input mass points often lack volume information. At this time, the ratio of the number of mass points to the number of grid nodes can be used as an estimate of the ratio of the volume corresponding to the mass point to the volume corresponding to the grid node. That is, the actual target interpolation function used is: , the spatial coordinate information of each finite element node Substituting this function, we can get the initial mass distribution model.

[0095] Step (4): Add up the masses of each node to get the total mass of the model , calculate the actual total mass of the wing and the aircraft The actual total mass It is not given directly, so it is obtained by inputting the total mass of the mass points, that is: .

[0096] Step (5): Use the obtained node masses As the weight, calculate the weighted average of the coordinates of each node to obtain the spatial position coordinates of the model's centroid ,in , , . The obtained model center of mass coordinates are compared with the center of mass coordinates of the aircraft wing By comparison, here we obtain the weighted average of the input mass point coordinates, namely: , , . Calculate the coordinates of the model's centroid The actual centroid The difference is used to determine whether the accuracy meets the standard and calculate the adjustment value.

[0097] Step (6): Using the obtained mass of each node, combined with the coordinates of each node and the coordinates of the model's center of mass, the X, Y, and Z axes of the model's rotational inertia are obtained. The specific calculation method is: , , Compare it with the actual moment of inertia of the component to be analyzed, which is obtained by calculating the moment of inertia of the input mass point, that is: , , The difference between the three-axis moment of inertia of the calculated model and the actual moment of inertia is used for subsequent accuracy determination and calculation of adjustment values.

[0098] Step (7): When the mass calculated from steps (4) to (6) , Centroid When the moment of inertia error does not meet the requirements, it is necessary to calculate the gradient of these parameters relative to the mass of each node to calculate the fine-tuning values ​​of subsequent iterations. The gradient of After obtaining the gradient, based on the difference between the actual total mass and the model total mass , we can get the mass demand adjustment of each node based on the total mass: Similarly, the mass demand adjustment of each node based on the centroid coordinates can be obtained: , , , and the required adjustment based on the moment of inertia , , .

[0099] Step (8): Calculate the actual adjustment by taking the weighted average of the required adjustment based on mass, center of mass coordinates, and moment of inertia:

[0100] ;

[0101] in, is the relative error of the total mass, , , is the relative error of the centroid coordinates, , , is the relative error of the moment of inertia. Add this adjustment to the existing mass of each node , and get the adjusted quality of each node .

[0102] Step (9): Repeat steps (4) to (8) until the total mass, center of mass position, and moment of inertia meet the corresponding accuracy requirements.

[0103] Step (10): Output the calculation results by writing all node numbers and their corresponding node masses to a file.

[0104] It can be seen that the present application discloses a method for constructing a mass distribution of a structural finite element model of an aircraft, comprising: obtaining mass point data of each mass point on a component to be analyzed of the aircraft and a finite element model file corresponding to the component to be analyzed; wherein the mass point is a discrete point used to characterize the inertia parameters and mass distribution of the component to be analyzed; determining a target interpolation function according to the mass point data and an interpolation function format, so as to calculate the initial mass distribution of each finite element node through the target interpolation function and according to the spatial coordinate information of each finite element node in the finite element model file; calculating the total mass of the finite element model of the component to be analyzed according to the initial mass distribution, and calculating the actual total mass of the component to be analyzed based on the mass point data, so as to calculate a first modeling error according to the total mass of the finite element model and the actual total mass, and calculating the first modeling error according to the total mass of the finite element model and the actual total mass of the component to be analyzed. The method comprises the following steps: calculating a second modeling error according to the centroid of the finite element model of the component to be analyzed and the actual centroid, calculating a third modeling error according to the moment of inertia of the finite element model of the component to be analyzed and the actual moment of inertia; performing gradient calculation on the finite element model information corresponding to the modeling error that does not meet the corresponding error requirement, so as to adjust the node initial mass of each finite element node according to the corresponding gradient information, and then jumping to execute the step of calculating the first modeling error according to the total mass of the finite element model and the actual total mass, until each modeling error meets the corresponding modeling requirement, and outputting the target mass distribution result of each corresponding finite element node; wherein the modeling error that does not meet the corresponding error requirement is any one or more of the first modeling error greater than the first error threshold, the second modeling error greater than the second error threshold, and the third modeling error greater than the third error threshold. It can be seen that through the target interpolation method, based on the given mass distribution measurement results, the corresponding finite element model node mass distribution results are calculated; and based on the conservation of the overall mass and moment of inertia of the model, the accuracy and reliability of the distribution results are determined; at the same time, based on the determination results, the mass distribution is fine-tuned and iterated until the accuracy meets the analysis requirements, and the use of interpolation and iterative fine-tuning realizes the automatic calculation and allocation of finite element mass distribution, which greatly improves the efficiency of structural finite element dynamics solution and its solution in aerodynamic / structural coupling analysis applications; by determining the accuracy of the distribution results based on a variety of mass distribution accuracy criteria and performing iterative fine-tuning accordingly, the accuracy and reliability of the mass distribution modeling results are guaranteed.

[0105] Reference Figure 7 As shown, the present invention also discloses a device for constructing mass distribution of a structural finite element model of an aircraft, comprising:

[0106] The information acquisition module 11 is used to obtain the mass point data of each mass point on the component to be analyzed of the aircraft and the finite element model file corresponding to the component to be analyzed; wherein the mass point is a discrete point used to characterize the inertia parameter and mass distribution of the component to be analyzed;

[0107] An initial calculation module 12, used to determine a target interpolation function according to the mass point data and the interpolation function format, so as to calculate the initial mass distribution of each finite element node according to the target interpolation function and the spatial coordinate information of each finite element node in the finite element model file;

[0108] an error acquisition module 13, configured to calculate the total mass of the finite element model of the component to be analyzed according to the initial mass distribution, and calculate the actual total mass of the component to be analyzed based on the mass point data, so as to calculate a first modeling error according to the total mass of the finite element model and the actual total mass, calculate a second modeling error according to the center of mass of the finite element model of the component to be analyzed and the actual center of mass, and calculate a third modeling error according to the moment of inertia of the finite element model of the component to be analyzed and the actual moment of inertia;

[0109] The quality adjustment module 14 is used to perform gradient calculation on the finite element model information corresponding to the modeling error that does not meet the corresponding error requirements, so as to adjust the initial node mass of each finite element node according to the corresponding gradient information, and then jump to execute the step of calculating the first modeling error according to the total mass of the finite element model and the actual total mass until each modeling error meets the corresponding modeling requirements, and output the corresponding target mass distribution results of each finite element node; wherein the modeling error that does not meet the corresponding error requirements is any one or more of the first modeling error greater than the first error threshold, the second modeling error greater than the second error threshold, and the third modeling error greater than the third error threshold.

[0110] It can be seen that the present application discloses obtaining mass point data of each mass point on a component to be analyzed of an aircraft and a finite element model file corresponding to the component to be analyzed; wherein the mass point is a discrete point used to characterize the inertia parameters and mass distribution of the component to be analyzed; determining a target interpolation function according to the mass point data and the interpolation function format, so as to calculate the initial mass distribution of each finite element node through the target interpolation function and according to the spatial coordinate information of each finite element node in the finite element model file; calculating the total mass of the finite element model of the component to be analyzed according to the initial mass distribution, and calculating the actual total mass of the component to be analyzed based on the mass point data, so as to calculate a first modeling error according to the total mass of the finite element model and the actual total mass, and calculating the first modeling error according to the center of mass of the finite element model of the component to be analyzed and the actual total mass. The second modeling error is calculated based on the center of mass, and the third modeling error is calculated based on the finite element model moment of inertia of the component to be analyzed and the actual moment of inertia; the finite element model information corresponding to the modeling error that does not meet the corresponding error requirement is gradient calculated to adjust the node initial mass of each finite element node according to the corresponding gradient information, and then the step of calculating the first modeling error based on the total mass of the finite element model and the actual total mass is jumped to execute until each modeling error meets the corresponding modeling requirement, and the target mass distribution result of each corresponding finite element node is output; wherein the modeling error that does not meet the corresponding error requirement is any one or more of the first modeling error greater than the first error threshold, the second modeling error greater than the second error threshold, and the third modeling error greater than the third error threshold. It can be seen that through the target interpolation method, based on the given mass distribution measurement results, the corresponding finite element model node mass distribution results are calculated; and based on the conservation of the overall mass and moment of inertia of the model, the accuracy and reliability of the distribution results are determined; at the same time, based on the determination results, the mass distribution is fine-tuned and iterated until the accuracy meets the analysis requirements, and the use of interpolation and iterative fine-tuning realizes the automatic calculation and allocation of finite element mass distribution, which greatly improves the efficiency of structural finite element dynamics solution and its solution in aerodynamic / structural coupling analysis applications; by determining the accuracy of the distribution results based on a variety of mass distribution accuracy criteria and performing iterative fine-tuning accordingly, the accuracy and reliability of the mass distribution modeling results are guaranteed.

[0111] Furthermore, the present application also discloses an electronic device. Figure 8 This is a structural diagram of an electronic device 20 according to an exemplary embodiment. The content in the diagram cannot be regarded as any limitation on the scope of use of the present application.

[0112] Figure 8A schematic diagram of the structure of an electronic device 20 provided in an embodiment of the present application. The electronic device 20 may specifically include: at least one processor 21, at least one memory 22, a power supply 23, a communication interface 24, an input / output interface 25, and a communication bus 26. The memory 22 is used to store a computer program, which is loaded and executed by the processor 21 to implement the relevant steps in the method for constructing the mass distribution of the structural finite element model of the aircraft disclosed in any of the aforementioned embodiments. In addition, the electronic device 20 in this embodiment may specifically be an electronic computer.

[0113] In this embodiment, the power supply 23 is used to provide working voltage for each hardware device on the electronic device 20; the communication interface 24 can create a data transmission channel between the electronic device 20 and the external device, and the communication protocol it follows is any communication protocol that can be applied to the technical solution of the present application, and is not specifically limited here; the input and output interface 25 is used to obtain external input data or output data to the outside world, and its specific interface type can be selected according to specific application needs and is not specifically limited here.

[0114] Among them, the processor 21 may include one or more processing cores, such as a 4-core processor, an 8-core processor, etc. The processor 21 can be implemented in at least one hardware form of DSP (Digital Signal Processing), FPGA (Field-Programmable Gate Array), and PLA (Programmable Logic Array). The processor 21 may also include a main processor and a coprocessor. The main processor is a processor for processing data in the awake state, also known as a CPU (Central Processing Unit); the coprocessor is a low-power processor for processing data in the standby state. In some embodiments, the processor 21 may be integrated with a GPU (Graphics Processing Unit), which is responsible for rendering and drawing the content to be displayed on the display screen. In some embodiments, the processor 21 may also include an AI (Artificial Intelligence) processor, which is used to process computing operations related to machine learning.

[0115] In addition, the memory 22, as a carrier for storing resources, can be a read-only memory, a random access memory, a disk or an optical disk, etc. The resources stored thereon can include an operating system 221, a computer program 222, etc., and the storage method can be temporary storage or permanent storage.

[0116] Among them, the operating system 221 is used to manage and control the hardware devices and computer programs 222 on the electronic device 20, so as to realize the operation and processing of the massive data 223 in the memory 22 by the processor 21, which can be Windows Server, Netware, Unix, Linux, etc. In addition to including a computer program that can be used to complete the method for constructing the mass distribution of the structural finite element model of the aircraft executed by the electronic device 20 disclosed in any of the aforementioned embodiments, the computer program 222 can further include a computer program that can be used to complete other specific tasks. In addition to data transmitted from an external device received by the electronic device, the data 223 can also include data collected by its own input and output interface 25, etc.

[0117] Furthermore, the present application also discloses a computer-readable storage medium for storing a computer program; wherein, when the computer program is executed by a processor, the aforementioned disclosed method for constructing a mass distribution of a structural finite element model of an aircraft is implemented. The specific steps of the method can be referred to the corresponding contents disclosed in the aforementioned embodiments, and will not be described in detail here.

[0118] In this specification, each embodiment is described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the embodiments can be referred to each other. For the device disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant parts can be referred to the method part.

[0119] Professionals may further appreciate that the units and algorithm steps of each example described in conjunction with the embodiments disclosed herein can be implemented with electronic hardware, computer software, or a combination of the two. In order to clearly illustrate the interchangeability of hardware and software, the composition and steps of each example have been generally described in terms of function in the above description. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Professional and technical personnel may use different methods to implement the described functions for each specific application, but such implementation should not be considered to be beyond the scope of this application. The steps of the method or algorithm described in conjunction with the embodiments disclosed herein can be implemented directly with hardware, a software module executed by a processor, or a combination of the two. The software module can be placed in a random access memory RAM (Random Access Memory), memory, read-only memory ROM (Read Only Memory), electrically programmable EPROM (Electrically Programmable Read Only Memory), electrically erasable programmable EEPROM (ElectricErasable Programmable Read Only Memory), register, hard disk, removable disk, CD-ROM (CompactDisc-Read Only Memory), or any other form of storage medium known in the technical field.

[0120] Finally, it should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

[0121] The scheme provided by the present invention is introduced in detail above. Specific examples are used in this article to illustrate the principle and implementation mode of the present invention. The description of the above embodiments is only used to help understand the method of the present invention and its core idea. At the same time, for those skilled in the art, according to the idea of ​​the present invention, there will be changes in the specific implementation mode and application scope. In summary, the content of this specification should not be understood as limiting the present invention.

Claims

1. A method for constructing mass distribution of a structural finite element model of an aircraft, characterized in that: include: Acquire mass point data of each mass point on the component to be analyzed of the aircraft and a finite element model file corresponding to the component to be analyzed; wherein the mass point is a discrete point used to characterize the inertia parameter and mass distribution of the component to be analyzed; Determining a target interpolation function according to the mass point data and the interpolation function format, so as to calculate the initial mass distribution of each finite element node according to the target interpolation function and the spatial coordinate information of each finite element node in the finite element model file; Calculating the total mass of the finite element model of the component to be analyzed according to the initial mass distribution, and calculating the actual total mass of the component to be analyzed based on the mass point data, so as to calculate a first modeling error according to the total mass of the finite element model and the actual total mass, calculate a second modeling error according to the center of mass of the finite element model of the component to be analyzed and the actual center of mass, and calculate a third modeling error according to the moment of inertia of the finite element model of the component to be analyzed and the actual moment of inertia; The finite element model information corresponding to the modeling error that does not meet the corresponding error requirement is gradient calculated to adjust the node initial mass of each finite element node according to the corresponding gradient information, and then jump to execute the step of calculating the first modeling error according to the total mass of the finite element model and the actual total mass until each modeling error meets the corresponding modeling requirement, and outputs the target mass distribution result of each corresponding finite element node; Among them, the modeling error that does not meet the corresponding error requirement is any one or more of the first modeling error greater than a first error threshold, the second modeling error greater than a second error threshold, and the third modeling error greater than a third error threshold.

2. The method for constructing a mass distribution of a structural finite element model of an aircraft according to claim 1, characterized in that: The step of obtaining mass point data of each mass point on the component to be analyzed of the aircraft and a finite element model file corresponding to the component to be analyzed includes: Obtaining the quantity information, actual mass information, and spatial coordinate information of each mass point on the component to be analyzed of the aircraft; A finite element model file corresponding to the component to be analyzed is obtained, so as to read the quantity information and the spatial coordinate information of each finite element node from the finite element model file.

3. The method for constructing a mass distribution of a structural finite element model of an aircraft according to claim 2, characterized in that: The step of determining a target interpolation function according to the mass point data and the interpolation function format, so as to calculate the initial mass distribution of each finite element node according to the target interpolation function and the spatial coordinate information of each finite element node in the finite element model file, comprises: Substituting the spatial coordinate information and the actual mass information of each mass point into the interpolation function format to determine the target interpolation function; The spatial coordinate information of each of the finite element nodes is substituted into the target interpolation function to calculate the initial mass distribution of each of the finite element nodes.

4. The method for constructing a mass distribution of a structural finite element model of an aircraft according to claim 2, characterized in that: The calculating the total mass of the finite element model of the component to be analyzed according to the initial mass distribution, and calculating the actual total mass of the component to be analyzed based on the mass point data, comprises: Accumulating the masses of each initial node in the initial mass distribution to calculate the total mass of the finite element model of the component to be analyzed; calculating the actual total mass of the component to be analyzed based on the actual mass information of each mass point; Calculate the model centroid coordinates of the finite element model using the mass of each of the initial nodes, the spatial coordinate information of each of the finite element nodes, and the total mass of the finite element model; calculate the actual centroid coordinates of the component to be analyzed using the actual mass information of each of the mass points, the spatial coordinate information of each of the mass points, and the actual total mass; The finite element model moment of inertia of the component to be analyzed is calculated using the mass of each of the initial nodes, the spatial coordinate information of each of the finite element nodes, and the model center of mass coordinates; the actual moment of inertia of the component to be analyzed is calculated using the actual mass information of each of the mass points, the spatial coordinate information of each of the mass points, and the actual center of mass coordinates.

5. The method for constructing a mass distribution of a structural finite element model of an aircraft according to claim 4, characterized in that: The first modeling error is calculated according to the total mass of the finite element model and the actual total mass, the second modeling error is calculated according to the center of mass of the finite element model of the component to be analyzed and the actual center of mass, and the third modeling error is calculated according to the moment of inertia of the finite element model of the component to be analyzed and the actual moment of inertia, including: Performing a difference processing on the total mass of the finite element model and the actual total mass to obtain a first modeling error; Performing a difference process on the model centroid coordinates and the actual centroid coordinates to obtain a second modeling error; The finite element model moment of inertia and the actual moment of inertia are subjected to difference processing to obtain a third modeling error.

6. The method for constructing a mass distribution of a structural finite element model of an aircraft according to claim 5, characterized in that: Also includes: When stiffness information and damping information exist in the finite element model file, solving the modal analysis result of the finite element model of the component to be analyzed; performing a difference process on the modal analysis result of the finite element model and the actual modal analysis result to obtain a fourth modeling error; Accordingly, the finite element model information corresponding to the modeling error that does not meet the corresponding error requirement is subjected to gradient calculation to adjust the node initial quality of each finite element node according to the corresponding gradient information, including: The finite element model information corresponding to the fourth modeling error that does not meet the corresponding error requirement is subjected to gradient calculation, so as to adjust the node initial quality of each finite element node according to the corresponding gradient information.

7. The method for constructing a mass distribution of a structural finite element model of an aircraft according to any one of claims 1 to 6, characterized in that: The step of adjusting the initial node quality of each finite element node according to the corresponding gradient information includes: Calculate a corresponding quality requirement adjustment amount based on a modeling error corresponding to the gradient information and the gradient information; The mass requirement adjustment amount is weighted averaged to obtain a corresponding target mass requirement adjustment amount; and the node initial mass of each finite element node is adjusted according to the target mass requirement adjustment amount.

8. A device for constructing mass distribution of a structural finite element model of an aircraft, characterized in that: include: An information acquisition module, used to acquire mass point data of each mass point on the component to be analyzed of the aircraft and a finite element model file corresponding to the component to be analyzed; wherein the mass point is a discrete point used to characterize the inertia parameter and mass distribution of the component to be analyzed; an initial calculation module, used to determine a target interpolation function according to the mass point data and the interpolation function format, so as to calculate the initial mass distribution of each finite element node according to the target interpolation function and the spatial coordinate information of each finite element node in the finite element model file; an error acquisition module, configured to calculate the total mass of the finite element model of the component to be analyzed according to the initial mass distribution, and calculate the actual total mass of the component to be analyzed based on the mass point data, so as to calculate a first modeling error according to the total mass of the finite element model and the actual total mass, calculate a second modeling error according to the centroid of the finite element model of the component to be analyzed and the actual centroid, and calculate a third modeling error according to the moment of inertia of the finite element model of the component to be analyzed and the actual moment of inertia; A quality adjustment module is used to perform gradient calculation on the finite element model information corresponding to the modeling error that does not meet the corresponding error requirements, so as to adjust the initial node mass of each finite element node according to the corresponding gradient information, and then jump to execute the step of calculating the first modeling error according to the total mass of the finite element model and the actual total mass until each modeling error meets the corresponding modeling requirements, and output the corresponding target mass distribution results of each finite element node; wherein the modeling error that does not meet the corresponding error requirements is any one or more of the first modeling error greater than the first error threshold, the second modeling error greater than the second error threshold, and the third modeling error greater than the third error threshold.

9. An electronic device, characterized in that: include: Memory, used to store computer programs; A processor is used to execute the computer program to implement the steps of the method for constructing the mass distribution of the structural finite element model of the aircraft as described in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that: Used to store computer programs; wherein, when the computer program is executed by a processor, the steps of the method for constructing the mass distribution of the structural finite element model of an aircraft as described in any one of claims 1 to 7 are implemented.

Images